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    INJECTION MANIFOLD WITH TESLA VALVES FOR ROTATING DETONATION ENGINES
    1.
    发明申请
    INJECTION MANIFOLD WITH TESLA VALVES FOR ROTATING DETONATION ENGINES 有权

    公开(公告)号：US20220195963A1

    公开(公告)日：2022-06-23

    申请号：US17553550

    申请日：2021-12-16

    申请人： Purdue Research Foundation

    发明人： Qili Liu ,  Li Qiao

    IPC分类号： F02K9/52 ,  F02C3/16 ,  F02C5/02 ,  F02K3/04 ,  F02K7/04 ,  F02K9/66

    摘要： A rotating detonation engine (RDE) is disclosed which includes a housing, an injector assembly disposed within the housing, the injector assembly includes a fuel manifold, an oxidizer manifold, and a combustion chamber, fuel from the fuel manifold and an oxidizer from the oxidizer manifold are combined and combusted in the combustion chamber, each of the fuel and oxidizer manifolds communicates with the combustion chamber via a plurality of Tesla valves each via a corresponding port, wherein the plurality of Tesla valves substantially eliminate reverse flow of exhaust gases from the combustion chamber back to the fuel manifold or the oxidizer manifold.

    Methods and apparatus for generating gas turbine engine thrust with a pulse detonation thrust augmenter
    3.
    发明授权
    Methods and apparatus for generating gas turbine engine thrust with a pulse detonation thrust augmenter 有权
    用脉冲爆震推力增强器产生燃气涡轮发动机推力的方法和装置

    公开(公告)号：US06883302B2

    公开(公告)日：2005-04-26

    申请号：US10326343

    申请日：2002-12-20

    申请人： John Michael Koshoffer

    发明人： John Michael Koshoffer

    IPC分类号： F02C5/10 ,  F02K1/00 ,  F02K3/075 ,  F02K3/08 ,  F02K7/04 ,  F02K7/06 ,  F02K7/075 ,  F23R7/00 ,  F02K7/02 ,  F02K3/10 ,  F02K3/105

    CPC分类号： F02K3/08 ,  F02K3/075 ,  F02K7/06 ,  F02K7/075

    摘要： A method enables thrust to be generated from a gas turbine engine using a pulse detonation system is provided. The engine includes an inlet portion and an exhaust portion, and the pulse detonation system includes a multi-staged pulse detonation augmentor including predetonator. The method comprises supplying a less than stoichiometric fuel/air mixture to the pulse detonation system during a first operating stage, detonating the fuel/air mixture with the predetonator to increase the temperature and pressure within the engine and to generate engine thrust, and supplying additional fuel and air to the pulse detonation system during a second operating stage.

    摘要翻译： 提供了一种使用脉冲爆震系统从燃气涡轮发动机产生推力的方法。 发动机包括入口部分和排气部分，并且脉冲爆震系统包括多级脉冲爆震增强器，包括预引导器。 该方法包括在第一操作阶段向脉冲爆震系统提供小于化学计量的燃料/空气混合物，用预蒸发器引爆燃料/空气混合物，以增加发动机内的温度和压力并产生发动机推力，并提供额外的 燃料和空气在第二操作阶段期间到脉冲爆震系统。

    Shock wave reflector and detonation chamber
    4.
    发明授权
    Shock wave reflector and detonation chamber 失效
    冲击波反射器和爆轰室

    公开(公告)号：US06877310B2

    公开(公告)日：2005-04-12

    申请号：US10107653

    申请日：2002-03-27

    申请人： Ivett Alejandra Leyva

    发明人： Ivett Alejandra Leyva

    IPC分类号： F02K7/02 ,  F02K7/04 ,  F23R7/00 ,  F02C5/00

    CPC分类号： F23R7/00 ,  F02K7/02 ,  F02K7/04

    摘要： A shock wave reflector includes a number of reflective units positioned along a longitudinal direction and separated by a gap G. Each reflective unit has a length L. The length L and the gap G are governed by a relationship L+G≧λ. The variable λ characterizes a cell size for a detonation mixture. A detonation chamber includes a receiving end, a discharge end, and a wall extending along a longitudinal direction between the receiving and discharge ends. The detonation chamber further includes a number of reflective units formed in the wall and positioned along the longitudinal direction. The reflective units are separated by a gap G, and each reflective unit has a length L.

    摘要翻译： 冲击波反射器包括沿着纵向方向定位并由间隙G分开的多个反射单元。每个反射单元具有长度L.长度L和间隙G由关系L + G> =λ控制。 变量lambda表征爆炸混合物的单元格大小。 爆震室包括接收端，放电端和沿着纵向方向在接收端和放电端之间延伸的壁。 引爆室还包括形成在壁中并沿纵向方向定位的多个反射单元。 反射单元被间隙G隔开，并且每个反射单元具有长度L.

    Pulse combusted acoustic agglomeration apparatus and process
    5.
    发明授权
    Pulse combusted acoustic agglomeration apparatus and process 失效
    脉冲燃烧声凝集装置及工艺

    公开(公告)号：US5197399A

    公开(公告)日：1993-03-30

    申请号：US730245

    申请日：1991-07-15

    申请人： Momtaz N. Mansour

    发明人： Momtaz N. Mansour

    IPC分类号： B01D45/12 ,  B01D49/00 ,  B01D51/08 ,  F01D25/00 ,  F02C7/30 ,  F02K7/04 ,  F23C15/00 ,  F23J15/00

    CPC分类号： F01D25/007 ,  B01D45/12 ,  B01D49/006 ,  B01D51/08 ,  F01D25/002 ,  F02C7/30 ,  F02K7/04 ,  F23C15/00 ,  F23J15/00

    摘要： An improved apparatus and process for removal of particulates entrained in a gas stream are provided. The removal process employs a pulse combustor to provide an acoustic pressure wave to acoustically enhance bimodal agglomeration of particulates which may be collected and removed using a conventional separation apparatus. A particulate having a size different from the size of the particulate in the gas stream to be cleaned is introduced into the system to effectuate the bimodal process. The apparatus may be employed as a direct fired system for improved operation of gas-operated equipment such as a gas turbine, or may, alternatively, be employed as an add-on subsystem for combustion exhaust clean-up. Additionally, the added particulate may be a sorbent for effecting sorption of other contaminants such as sulfur. Various other particulates for contaminant removal may also be introduced into the system as exemplified by alkali-gettering agents.

    摘要翻译： 提供了用于去除夹带在气流中的微粒的改进的装置和方法。 去除过程采用脉冲燃烧器来提供声压波，以声学增强可以使用常规分离装置收集和去除的微粒的双峰聚集。 将具有不同于待清洁的气流中的颗粒尺寸的颗粒的颗粒引入到系统中以实现双峰过程。 该装置可以用作直接燃烧系统，以改进诸如燃气轮机的气体操作设备的操作，或者可以用作用于燃烧排气净化的附加子系统。 另外，添加的颗粒可以是用于吸附其它污染物例如硫的吸附剂。 用于除去污染物的各种其它颗粒也可以引入到系统中，例如碱吸除剂。

    Pulse jet engine
    6.
    发明授权
    Pulse jet engine 失效
    脉冲喷气发动机

    公开(公告)号：US4962641A

    公开(公告)日：1990-10-16

    申请号：US316854

    申请日：1989-02-28

    申请人： John N. Ghougasian

    发明人： John N. Ghougasian

    IPC分类号： F02K7/04 ,  F02K7/06

    CPC分类号： F02K7/06 ,  F02K7/04

    摘要： Combustion supporting air in the resonator tube of a pulse jet engine is cyclically compressed by combustion and discharged through a decelerating passage of a diffuser in a tail section of the engine to internally pressurize an afterbody preceding atmospheric dishcarge of the combustion products through nozzle passages, followed by primary refill with air from the pressurized afterbody and secondary refill by reentry of external air. The nozzle passages are formed in angularly spaced, rearwardly diverging vane formations of the tail section projecting from a protective casing directing ram air intake into orifice openings formed in a rear end portion of the diffuser to regulate afterbody pressurization under control of ram pressure created by forward propulsion of the engine.

    摘要翻译： 在脉冲喷气发动机的谐振管中的燃烧支持空气通过燃烧循环地压缩并通过发动机尾部的扩散器的减速通道排出，以通过喷嘴通道在内部对燃烧产物的大气压力之前的体内加压，随后 通过主要再充填来自加压后身体的空气和通过外部空气的再入进行二次充填。 喷嘴通道形成在从形成在扩散器的后端部分的孔口中的保护壳体的保护壳体上形成的角度间隔开的向后扩散的叶片结构中，所述保护壳体引导形成在扩散器的后端部分中的孔口开口，以在由向前产生的压头压力的控制下调节后体加压 发动机推进。

    Intermittent combustion device with a pair of coextensive and coaxial mutually inductive chambers
    7.
    发明授权
    Intermittent combustion device with a pair of coextensive and coaxial mutually inductive chambers 失效
    具有一对共同和同轴电机的间歇式燃烧装置

    公开(公告)号：US3824787A

    公开(公告)日：1974-07-23

    申请号：US29074072

    申请日：1972-09-20

    申请人： ETESSAM A

    发明人： ETESSAM A

    IPC分类号： F02K7/075 ,  F02K7/04

    CPC分类号： F02K7/075

    摘要： A gas generator for a turbine or jet power plant comprising a pair of coextensive combustion chambers normally coaxially arranged between the inlet and outlet and each operating on the pulse jet principle, the combustion chambers converging towards the outlet in the form of mutually inductive nozzles so that the combustion chambers operate in an alternate cycle providing continuous throughput of air from inlet to outlet. Embodiments include power plants incorporating the combustion chambers and suitable for stationary purposes such as road vehicles, subsonic aircraft and supersonic aircraft, turbine and bypass engines.

    摘要翻译： 一种用于涡轮或喷气动力装置的气体发生器，包括一对共同延伸的燃烧室，通常同轴地布置在入口和出口之间，并且各自以脉冲喷射原理运行，燃烧室以相互感应的喷嘴的形式会聚到出口，使得 燃烧室以交替的循环运行，从而从进口到出口连续提供空气的产量。 实施例包括结合有燃烧室并适用于固定目的的发电厂，例如道路车辆，亚音速飞机和超音速飞机，涡轮机和旁路引擎。